FIELD: turbojet engines.
SUBSTANCE: invention relates to turbojet engines and can be used to create vehicles capable of moving in the aquatic environment, in the air and in outer space. A turbojet engine consists of an engine housing (1), a compressor turbine (3) and a high pressure turbine (4) that are located on slide bearings (6). There is the main alternator (16) on the outer shaft (2). The main alternator (16) has a bias generator (17) and an alternator (15) of an electromagnetic clutch with an armature connected with the axis (30) of the gearbox (29). There is a combined thermal combustion chamber inside the housing (1). The chamber has a combustion chamber (48), an air intake chamber (36), a chamber (42) heating air with a heating element (53) mounted on ceramic partitions (55). Spray nozzles (52) with electrodes are installed in the channel. There are a condenser (25) and a compressor (28) of the cooling system inside the air duct, and a reducer (29) is installed on the outside of the air duct. The thermal combustion chamber additionally contains rocket engines (34) using liquid rocket fuel. There is a fairing (37) inside the air intake chamber (36) secured by power partitions (38) with it. There is a pneumatic cylinder (39) inside the fairing (37). The pneumatic cylinder is connected by a pipeline (40) to the air pipe . The air intake chamber (36) is connected by strengthening ribs (41) (43) with the air heating chamber (42) and with the channel (43) which contains a damper (44). The damper limits the air flow from the propeller turbine (3) of the compressor into the air intake chamber (36). A check valve (46) is installed on the air heating chamber (42), which is connected by pipeline (47) to the air line solenoid valve. The combustion chamber (48) consists of an outer casing connected with the channel outlet (50). An expanding nozzle is located at the channel outlet (50) and inside the casing of the combustion chamber (48). There are refractory rings (57) of different diameters on the widened edge of the expanding nozzle. The refractory rings are fixed to each other. The outlet of the combustion chamber (48) is directed to the hollow blades (23) of the high pressure turbine (4). There is a channel (50) between the combustion chamber (48) and the air heating chamber (42) and this channel contains a blade (49).
EFFECT: invention enables the engine to operate in outer space and in the aquatic environment while maintaining the increased power of the turbojet engine and reducing fuel consumption.
4 cl, 9 dwg
